EP2550374A1 - Couche d'accrochage ou alliage métallique ayant une température de transition / ' élevée et un composant - Google Patents

Couche d'accrochage ou alliage métallique ayant une température de transition / ' élevée et un composant

Info

Publication number
EP2550374A1
EP2550374A1 EP10710755A EP10710755A EP2550374A1 EP 2550374 A1 EP2550374 A1 EP 2550374A1 EP 10710755 A EP10710755 A EP 10710755A EP 10710755 A EP10710755 A EP 10710755A EP 2550374 A1 EP2550374 A1 EP 2550374A1
Authority
EP
European Patent Office
Prior art keywords
alloy
coating
metallic coating
alloy according
preceeding
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP10710755A
Other languages
German (de)
English (en)
Inventor
Anand A. Kulkarni
Jonathan E. Shipper
Werner Stamm
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP2550374A1 publication Critical patent/EP2550374A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D1/00—Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a metallic bondcoat with phases of ⁇ and ⁇ ' a component.
  • Components for the hot gas path in gas turbines are made from Ni- or Co based materials. These materials are optimized for strength and are not able to withstand oxidation and/or corrosion attack at higher temperatures. Therefore, these kinds of materials must be protected against oxidation by MCrAIY-coatings which can be used as bondcoats for thermal barrier coating (TBC) systems as well. I n TBS systems, the MCrAIY coating is needed against hot gas attack on one side and on the other side this coating is needed to adhere the TBC to the substrate. Improving such systems against oxidation will lead to increased bondcoats service
  • MCrAIY overlay coatings are coated mainly by low pressure plasma spraying (LPPS), air plasma spraying (APS), electron beam physical vapor deposition (EBPVD), cold spray (CS) or high velocity oxy-fuel (HVOF) process.
  • LPPS low pressure plasma spraying
  • APS air plasma spraying
  • EBPVD electron beam physical vapor deposition
  • CS cold spray
  • HVOF high velocity oxy-fuel
  • the MCrAIY coating is based on nickel and/or cobalt, chromium, aluminum, silicon, rhenium and rare earth elements like yttrium.
  • With increasing bondcoat temperatures these coatings can fail which can lead to spallation of the thermal barrier coating. Therefore, with increasing service temperatures, improved coatings are needed to withstand the oxidation attack. Additionally this kind of coatings should have acceptable thermo-mechanical properties. These requests can only be achieved by an optimized composition of the bond coat.
  • figure 3 a turbine blade
  • figure 4 a gas turbine
  • figure 5 a list of super alloys.
  • Figure 3 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
  • the blade or vane 120, 130 has, in succession along the longitudinal axis 121 , a securing region 400, an adjoining blade or vane platform 403 and a main blade or vane part 406 as well as a blade or vane tip 415.
  • the vane 130 may have a further platform (not shown) at its vane tip 415.
  • a blade or vane root 183 which is used to secure the rotor blades 120, 130 to a shaft or disk (not shown), is formed in the securing region 400.
  • the blade or vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir-tree or dovetail root, are possible.
  • the blade or vane 120, 130 has a leading edge 409 and a trailing edge 412 for a medium which flows past the main blade or vane part 406.
  • the blade or vane 120, 130 may in this case be produced by a casting process, also by means of directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses.
  • Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
  • dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal.
  • a transition to globular (poiycrystalline) solidification needs to be avoided, since non- directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
  • directionally solidified microstructures refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries.
  • This second form of crystalline structures is also described as directionally solidified microstructures (directionally solidified structures).
  • the blades or vanes 120, 130 may likewise have coatings protecting against corrosion or oxidation, e.g. MCrAlX (M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and/or silicon and/or at least one rare earth element, or hafnium (Hf)). Alloys of this type are known from EP 0 486 489 B1 ,
  • EP 0 788 017 B1 , EP 0 412 397 B1 or EP 1 308 454 A1 which are intended to form part of the present disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • a protective aluminum oxide layer forms on the MCrAlX layer (as an intermediate layer or an outermost layer).
  • a thermal barrier coating consisting for example of Zr0 2 , Y 2 O 3 -ZrO 2 , i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or one or more of rare earth element (lanthanum, gadolinium, yttrium, etc.), which is preferably the outermost layer, to be present on the MCrAIX.
  • the thermal barrier coating covers the entire MCrAIX layer.
  • Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
  • EB-PVD electron beam physical vapor deposition
  • the thermal barrier coating may include porous grains which have microcracks or macrocracks for improving its resistance to thermal shocks.
  • the thermal barrier coating is therefore preferably more porous than the MCrAIX layer.
  • the blade or vane 120, 130 may be hollow or solid in form. If the blade or vane 120, 130 is to be cooled, it is hollow and may also have film-cooling holes 418 (indicated by dashed lines).
  • Figure 4 shows, by way of example, a partial longitudinal section through a gas turbine 100.
  • the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102, has a shaft 101 and is also referred to as the turbine rotor.
  • the annular combustion chamber 110 is in communication with a, for example, annular hot-gas passage 11 1 , where, by way of example, four successive turbine stages 1 12 form the turbine 108.
  • Each turbine stage 1 12 is formed, for example, from two blade or vane rings. As seen in the direction of flow of a working medium 1 13, in the hot-gas passage 11 1 a row of guide vanes 115 is followed by a row 125 formed from rotor blades 120.
  • the guide vanes 130 are secured to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are fitted to the rotor 103 for example by means of a turbine disk 133.
  • a generator (not shown) is coupled to the rotor 103.
  • the compressor 105 While the gas turbine 100 is operating, the compressor 105 sucks in air 135 through the intake housing 104 and compresses it. The compressed air provided at the turbine-side end of the compressor 105 is passed to the burners 107, where it is mixed with a fuel. The mix is then burnt in the combustion chamber 1 10, forming the working medium 1 13. From there, the working medium 113 flows along the hot-gas passage 1 1 1 past the guide vanes 130 and the rotor blades 120. The working medium 1 13 is expanded at the rotor blades 120, transferring its momentum, so that the rotor blades 120 drive the rotor 103 and the latter in turn drives the generator coupled to it.
  • Substrates of the components may likewise have a directional structure, i.e. they are in single-crystal form (SX structure) or have only longitudinally oriented grains
  • iron-based, nickel-based or cobalt-based superalloys are used as material for the components, in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 1 10.
  • the guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head at the opposite end from the guide vane root.
  • the guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143.
  • Tantalum (Ta) stabilizes the formation of a three phase system ( ⁇ '/ ⁇ / ⁇ ) with a high ⁇ '/ ⁇ transition temperature (see fig. 2). This will reduce the local stresses as well because tantalum (Ta) will stabilize the high transition temperatures of ⁇ ' which is higher than the bondcoat service temperature.
  • hafnium (Hf), silicon (Si) or zirconium (Zr) in the coating there is preferably no need for hafnium (Hf), silicon (Si) or zirconium (Zr) in the coating.
  • a composition (Ni-25Co-17Cr-10AI-1 .5Re-Y) which contains rhenium (Re) instead of tantalum (Ta) has a lower ⁇ 7 ⁇ transition temperature because no tantalum is added (see Fig. 1 ).
  • the bondcoat is preferably a nickel (Ni) based super alloy with addition of cobalt (Co), chromium (Cr), aluminum (Al) and optionally yttrium (Y) which is preferably consisting of these elements.
  • the alloy contains no molybdenum (Mo), and/or no tungsten (W) and/or columbium (Nb).
  • Mo molybdenum
  • W tungsten
  • Nb columbium

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Wood Science & Technology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Physical Vapour Deposition (AREA)

Abstract

Selon la présente invention, un ajout de tantale sur un revêtement à base de nickel stabilise les phases gamma/gamma' à des températures élevées, ce qui conduit à une réduction des contraintes locales.
EP10710755A 2010-03-23 2010-03-23 Couche d'accrochage ou alliage métallique ayant une température de transition / ' élevée et un composant Withdrawn EP2550374A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2010/028220 WO2011119145A1 (fr) 2010-03-23 2010-03-23 Couche d'accrochage ou alliage métallique ayant une température de transition γ/γ' élevée et un composant

Publications (1)

Publication Number Publication Date
EP2550374A1 true EP2550374A1 (fr) 2013-01-30

Family

ID=43663499

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10710755A Withdrawn EP2550374A1 (fr) 2010-03-23 2010-03-23 Couche d'accrochage ou alliage métallique ayant une température de transition / ' élevée et un composant

Country Status (7)

Country Link
US (1) US9133345B2 (fr)
EP (1) EP2550374A1 (fr)
JP (1) JP5615970B2 (fr)
KR (1) KR101661384B1 (fr)
CN (1) CN102822365B (fr)
RU (1) RU2523185C2 (fr)
WO (1) WO2011119145A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120128526A1 (en) * 2010-11-24 2012-05-24 Kulkarni Anand A Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component
EP2857638A1 (fr) * 2013-10-02 2015-04-08 Siemens Aktiengesellschaft Composant d'une turbomachine et procédé de construction du composant
CN107849672B (zh) * 2015-09-14 2021-03-02 三菱动力株式会社 涡轮动叶片的制造方法
KR20190052053A (ko) * 2016-09-12 2019-05-15 지멘스 악티엔게젤샤프트 Nicocraly-합금, 분말 및 층 시스템

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55161041A (en) * 1979-05-29 1980-12-15 Howmet Turbine Components Covering material
US4447503A (en) * 1980-05-01 1984-05-08 Howmet Turbine Components Corporation Superalloy coating composition with high temperature oxidation resistance
US4447603A (en) 1981-02-04 1984-05-08 American Cyanamid Company Substituted-6-n-propyl-8-methylimidazo[1,5-d]-as-triazin-4-(3H)-ones
DE3148198A1 (de) 1981-12-05 1983-06-09 Brown, Boveri & Cie Ag, 6800 Mannheim "hochtemperaturschutzschicht"
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
JP2773050B2 (ja) 1989-08-10 1998-07-09 シーメンス アクチエンゲゼルシヤフト 耐熱性耐食性の保護被覆層
US5316866A (en) * 1991-09-09 1994-05-31 General Electric Company Strengthened protective coatings for superalloys
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
GB9903988D0 (en) * 1999-02-22 1999-10-20 Rolls Royce Plc A nickel based superalloy
DE50006694D1 (de) 1999-07-29 2004-07-08 Siemens Ag Hochtemperaturbeständiges bauteil und verfahren zur herstellung des hochtemperaturbeständigen bauteils
RU2213802C2 (ru) * 2001-09-28 2003-10-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" Способ нанесения покрытий на сплавы
DE50104022D1 (de) 2001-10-24 2004-11-11 Siemens Ag Rhenium enthaltende Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung
EP1876263B1 (fr) * 2005-03-28 2014-05-14 National Institute for Materials Science Element resistant a la chaleur
CA2602716A1 (fr) 2005-03-29 2006-10-05 Banyu Pharmaceutical Co., Ltd. Agent therapeutique pour maladie adipeuse hepatique non alcoolique, et methode de selection de compose candidat medicamenteux pour le traitement ou la prevention de maladie adipeuse hepatique non alcoolique
US7341427B2 (en) * 2005-12-20 2008-03-11 General Electric Company Gas turbine nozzle segment and process therefor
JP5146867B2 (ja) * 2006-08-18 2013-02-20 独立行政法人物質・材料研究機構 高温耐久性に優れた耐熱部材
WO2008032806A1 (fr) * 2006-09-13 2008-03-20 National Institute For Materials Science Élément résistant à la chaleur
US8641963B2 (en) * 2008-07-08 2014-02-04 United Technologies Corporation Economic oxidation and fatigue resistant metallic coating
EP2145968A1 (fr) * 2008-07-14 2010-01-20 Siemens Aktiengesellschaft Superalliage renforcé d'amorce de gamme à base de nickel
RU2521925C2 (ru) * 2010-03-23 2014-07-10 Сименс Акциенгезелльшафт Металлическое связующее покрытие с высокой гамма/гамма' температурой перехода и компонент

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011119145A1 *

Also Published As

Publication number Publication date
CN102822365A (zh) 2012-12-12
JP5615970B2 (ja) 2014-10-29
US20130136648A1 (en) 2013-05-30
KR101661384B1 (ko) 2016-09-29
US9133345B2 (en) 2015-09-15
JP2013522474A (ja) 2013-06-13
KR20130051442A (ko) 2013-05-20
RU2012144794A (ru) 2014-04-27
CN102822365B (zh) 2016-01-20
WO2011119145A1 (fr) 2011-09-29
RU2523185C2 (ru) 2014-07-20

Similar Documents

Publication Publication Date Title
US9856545B2 (en) Metallic bondcoat with a high γ/γ' transition temperature and a component
US8057924B2 (en) Layer system comprising two pyrochlore phases
US20130243642A1 (en) Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component
US9556748B2 (en) Layer system with double MCrAlX metallic layer
CA2541289A1 (fr) Systeme multicouches
US8278232B2 (en) Pyrochlore materials and a thermal barrier coating with these pyrochlore materials
KR20140094659A (ko) 합금, 보호층 및 부품
US9133345B2 (en) Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component
US20130302638A1 (en) Alloy, protective layer and component
KR20190076070A (ko) 합금, 보호층 및 부품
US9435222B2 (en) Layer system having a two-ply metal layer
EP2622110B1 (fr) Couche d'accrochage métallique ou alliage ayant une température de transition gamma/gamma' élevée et un composant
US20130288072A1 (en) Alloy, protective layer and component
JP2015034344A (ja) γ／γ’転移温度の高い金属ボンドコート及び部品

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20120904

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20130723

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20200208